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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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A
747-400 MAINTENANCE MANUAL
Captain's Pitot-Static System (Fig. 2)
1) Pitot pressure is sensed from the pitot tube in the upper left pitot-static probe and is supplied to the left air data computer pitot input.
2) Static pressure is sensed from a set of static pressure ports on the upper left pitot-static probe cross-connected with a pair of static pressure ports on the lower right pitot-static probe. Static pressure is supplied to the left air data computer static input.
First Officer's Pitot-Static System (Fig. 2)
1) Pitot pressure is sensed from the pitot tube in the upper right pitot-static probe and is supplied to the right air data computer pitot input.
2) Pitot pressure is also supplied to the secondary input of the pitot-static source select valve as an alternate pitot source for the center air data computer.
3) Static pressure is sensed from a set of static pressure ports on the upper right pitot-static probe cross-connected with a pair of static pressure ports on the lower left pitot-static probe. Static pressure is supplied to the right air data computer static input.
Auxiliary No. 1 Pitot-Static System (Fig. 2)
1) Pitot pressure is sensed from the pitot tube in the lower left pitot-static probe and is supplied to the standby airspeed indicator and to the elevator feel computer left side pitot input.
2) Static pressure is sensed from a set of static pressure ports on the lower right pitot-static probe cross-connected with a pair of static pressure ports on the upper left pitot-static probe. Static pressure is supplied to the primary static input of the pitot-static source select valve as the normal static input to the center air data computer.
Auxiliary No. 2 Pitot-Static System (Fig. 2)
1) Pitot pressure is sensed from the pitot tube in the lower right pitot-static probe and is supplied to the elevator feel computer right side pitot input.
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
2) Pitot pressure is also supplied to the primary pitot input of the pitot-static source select valve as the normal pitot source for the center air data computer.
3) Static pressure is sensed from a set of static pressure ports on the lower left pitot-static probe cross-connected with a pair of static pressure ports on the upper right pitot-static probe. Static pressure is supplied to the secondary input of the pitot-static source select valve as an alternate static source for the center air data computer.
(g) Alternate Static System (Fig. 2) 1) The alternate static ports are mounted flush with the airplane skin and care is taken to see that no roughness exists on the surface of the skin to disturb air flow and compromise the ambient pressure in that area. To further assure accurate ambient pressure sensing, static pressure inputs are equalized by cross-connecting the ports on each side of the airplane. At each port, pressure is sensed through small holes which open into the alternate static source tubing.
2) The alternate static pressure ports provide static pressure to the standby altimeter and standby airspeed indicator.
(h) Dedicated Static Systems (Fig. 2) 1) The dedicated static ports are mounted flush with the airplane skin and care is taken to see that no roughness exists on the surface of the skin to disturb air flow and compromise the ambient pressure in that area. At the left port, pressure is sensed through small holes which open into the left dedicated static source tubing. At the right port, pressure is sensed throught small holes which open into the right dedicated static source tubing. 2) The left dedicated static pressure port provides static pressure to the elevator feel computer left side static input.
3) The right dedicated static pressure port provides static pressure to the elevator feel computer right side static input.
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